Apparatus and method for externally loaded liquid fuel injection for lean prevaporized premixed and dry low nox combustor

Abstract

A fuel injector stick for a gas turbine includes: a body of a length, L, the body including an annular shape forming a fuel channel and adapted for insertion into a premixer of the gas turbine; a mounting section for mounting the injector stick to the gas turbine; and a nozzle for injecting fuel into the premixer of the gas turbine. A gas turbine combustor and a method for changing fuel injector sticks are provided.

1 . A fuel injector stick for a gas turbine combustor, the fuel injector stick comprising:
 a body of a length, L, the body comprising an annular shape forming a fuel channel and adapted for insertion into a premixer of the gas turbine;   a mounting section for mounting the injector stick to the gas turbine combustor; and   a nozzle for injecting fuel into the premixer of the gas turbine combustor.   
   
   
       2 . The fuel injector stick as in  claim 1 , wherein an outer portion of the body comprises threads. 
   
   
       3 . The fuel injector stick as in  claim 1 , wherein an external surface of the body comprises a flat portion for mating with a washer comprising a flat portion on an inner circumference. 
   
   
       4 . The fuel injector stick as in  claim 3 , wherein the washer comprises a key for fitting into a keyway. 
   
   
       5 . The fuel injector stick as in  claim 1 , wherein the fuel injector stick comprises a design for delivering a type of fuel. 
   
   
       6 . The fuel injector stick as in  claim 1 , wherein the nozzle of the fuel injector stick is interchangeable. 
   
   
       7 . The fuel injector stick as in  claim 1 , wherein the mounting section is adapted for mounting a fuel supply line. 
   
   
       8 . A gas turbine combustor comprising:
 a plurality of fuel injector sticks disposed therein, each of the plurality comprising a body of a length, L, the body comprising an annular shape forming a fuel channel and adapted for insertion into a premixer of the gas turbine combustor; a mounting section for mounting the fuel injector stick; and a nozzle for injecting fuel into the premixer of the gas turbine combustor.   
   
   
       9 . The gas turbine combustor as in  claim 8 , wherein the plurality of fuel injector sticks are distributed concentrically about an axis of rotation for a premix nozzle. 
   
   
       10 . The gas turbine combustor as in  claim 8 , comprising a design for at least one of a dry-low-NO x  design and a lean prevaporized premixed design. 
   
   
       11 . The gas turbine combustor as in  claim 8 , wherein the gas turbine combustor comprises a can-annular gas turbine combustor. 
   
   
       12 . The gas turbine combustor as in  claim 8 , wherein at least one of the fuel injector sticks is disposed through an endcover of the gas turbine combustor. 
   
   
       13 . The gas turbine combustor as in  claim 8 , wherein an endcover comprises a plurality of keyways, each keyway adapted for securing one of the fuel injector sticks into the endcover. 
   
   
       14 . The gas turbine combustor as in  claim 8 , wherein a design for the plurality of fuel injector sticks provides for homogeneous mixing, which occurs quickly during operation. 
   
   
       15 . The gas turbine combustor as in  claim 8 , wherein a fuel supply is external to the gas turbine combustor. 
   
   
       16 . The gas turbine combustor as in  claim 8 , wherein the fuel injector stick comprises a design type that is one of a pressure swirl, jet swirl, a fan, a plain jet or an effervescent atomizer. 
   
   
       17 . The gas turbine combustor as in  claim 8 , wherein at least one of the fuel injector sticks comprises threads for securing the body into the gas turbine. 
   
   
       18 . The gas turbine combustor as in  claim 8 , wherein at least one of an endcover and the premixer comprises threads for retaining at least one of the fuel injector sticks. 
   
   
       19 . A method for changing fuel in a can-annular gas turbine combustor, the method comprising:
 selecting the fuel for the gas turbine combustor,   removing at least one fuel injector stick inserted into a premixer of the gas turbine, each stick comprising a body of a length, L, of an annular shape forming a fuel channel, a mounting section for mounting the injector stick to an endcover of the gas turbine combustor, and a nozzle for injecting fuel into the premixer of the gas turbine combustor; and   replacing the at least one fuel injector stick with another at least one fuel injector stick designed for dispensing the selected fuel.